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An analysis of the current Northrop helicopter obstacle avoidance system (OASYS) prototype with a fixed forward mounting, 25 x 50 degree field of view, 860 nanometer wavelength LADAR, was conducted to determine system effectiveness during simulated aircraft level accelerations ranging from 0 to 100 knots, and at accelerations rates of 0 to 2.9 meters/sec (2). Computer simulation flights were conducted using flight parameter data recorded at the Army Aeroflightdynamics Directorate Crew Station Research and Development Facility's (CSRDF) advanced concepts flight simulator. A multiple-program computer simulation was used to model the helicopter and sensor dynamics over a tactical data base of numerous obstacles consisting of trees, wires and poles; the resulting window of safety (WOS) displays were analyzed by comparing each acceleration maneuver with a control maneuver in which the sensor was horizon stabilized. A mathematical model of the flight maneuvers for which the OASYS prototype operated effectively was then determined based on the results of these simulations. The limits of this analytical flight envelope were then verified experimentally via a series of computer simulations using generalized maneuvers conducted over a standardized obstacle database.

The Naval Postgraduate School (NPS) currently has no laboratory facilities to support the teaching of flight mechanics. This thesis concerns a feasibility study con- ducted to define the need for a flight mechanics laboratory ...

This thesis research developed comparative analysis models to explore whether too many or too few flight hours affected the likelihood of a mishap. The objective was to determine whether the period of sequestration and the ...